US20160258305A1 - Vane for jet engine mid-turbine frame - Google Patents
Vane for jet engine mid-turbine frame Download PDFInfo
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- US20160258305A1 US20160258305A1 US15/032,017 US201515032017A US2016258305A1 US 20160258305 A1 US20160258305 A1 US 20160258305A1 US 201515032017 A US201515032017 A US 201515032017A US 2016258305 A1 US2016258305 A1 US 2016258305A1
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- annular structure
- segment portion
- mtf
- segment
- vane
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present disclosure relates to a vane for a jet engine mid-turbine frame, and more particularly, to a vane for a jet engine mid-turbine frame vane segment.
- Gas turbine engines generally include a compressor to pressurize inflowing air, a combustor to burn a fuel in the presence of the pressurized air, and a turbine to extract energy from the resulting combustion gases.
- the compressor may comprise a low pressure compressor, as well as a high pressure compressor.
- the turbine may likewise comprise a high pressure turbine and a low pressure turbine.
- an apparatus comprising a radially outward segment portion, a radially inward segment portion, and a vane that extends between the radially outward segment portion and the radially inward segment portion.
- a mid-turbine frame (“MTF”) for a jet engine comprising a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure is situated radially inward of the outer annular structure and a vane that extend radially outward from the inner annular structure through the outer annular structure.
- HPT high pressure turbine
- LPT low pressure turbine
- FIG. 1 illustrates, in accordance with various embodiments, a cutaway view of a jet engine
- FIG. 2 illustrates, in accordance with various embodiments, a cross-sectional view of portion of a jet engine turbine
- FIG. 3 illustrates, in accordance with various embodiments, a cutaway view of a MTF
- FIG. 4 illustrates, in accordance with various embodiments, a perspective view of vanes of an MTF
- FIG. 5 illustrates, in accordance with various embodiments, a further perspective view of vanes of an MTF.
- aft refers to the direction associated with the tail (e.g., the back end) of an aircraft, or generally, to the direction of exhaust of the gas turbine.
- forward refers to the directed associated with the nose (e.g., the front end) of an aircraft, or generally, to the direction of flight or motion.
- central axis A-A′ may be described as extending from a forward position (A) to an aft position (A′).
- a gas turbine engine may comprise a high pressure turbine and a low pressure turbine. Hot gas from a combustion section of a gas turbine engine may flow into the high pressure turbine and the low pressure turbine, in that order, from forward to aft. The kinetic energy of the hot gas is captured by the high pressure turbine and the low pressure turbine and converted into more other useful forms of energy. High pressure turbines tend to operate at maximum efficiency when the gas is hot and the high pressure turbine is small. Low pressure turbines tend to work at maximum efficiency when the hot gases operate at the low pressure turbine's largest diameter. Thus, for improved efficiency, there may be a large difference in the diameter between a high pressure turbine and a low pressure turbine. Conventionally, the forward stages of the low pressure turbine were not as efficient as they could be.
- gas turbine engines 100 may extend from forward to aft along a central axis A-A′.
- gas turbine engines 100 generally include a compressor to pressurize inflowing air, a combustor to burn a fuel in the presence of the pressurized air, and a turbine to extract energy from the resulting combustion gases.
- the compressor may be divided into two sections. Specifically, the compressor may comprise a low pressure compressor 102 situated forward of a high pressure compressor 104 .
- the turbine may likewise be divided into two sections. These include a high pressure turbine (or “HPT”) 106 situated forward of a low pressure turbine (or “LPT”) 108 .
- the combustor 110 may be disposed axially aft of the HPT 106 and axially forward of the LPT 108 .
- a structure which may be referred to herein as a “mid-turbine frame” or “MTF” 112 may be included as part of the gas turbine engine 100 . More particularly, as shown with respect to FIG. 2 , the MTF 112 may be disposed aft of the HPT 106 and forward of the LPT 108 .
- the MTF 112 may generally comprise a duct configured to convey (hot) combustion gasses from the HPT 106 to the LPT 108 .
- the MTF 112 may thus comprise an annular and/or semi-annular duct configured, in particular, to permit the expansion of hot gasses exiting the HPT 106 into the LPT 108 .
- the MTF 112 may enlarge in diameter as it extends from forward to aft along the central axis A-A′.
- the MTF 112 may more particularly comprise a plurality of segments (e.g., to illustrate a portion of an MTF 112 , a first segment 302 and second segment 304 ) that together form an MTF 112 .
- the first segment 302 and the second segment 304 may comprise radially outer arcing surfaces and radially inner arcing surfaces that may be joined or sealed, as described herein, to form an outer annular structure 306 and an inner annular structure 308 of an MTF 112 .
- first segment 302 and second segment 304 comprise arc segments that, when coupled, form outer annular structure 306 and inner annular structure 308 , wherein outer annular structure 306 is radially farther from central axis A-A′ than inner annular structure 308 .
- first segment 302 may comprise an outer arcing surface 330 a and an inner arcing surface 330 b
- second segment 304 may comprise an outer arcing surface 332 a and an inner arcing surface 332 b
- Outer arcing surface 332 a may be coupled to a radially outward segment portion.
- Inner arcing surface 332 b may be coupled to a radially inward segment portion.
- a radially inward segment portion may refer to a portion of a segment, such as segment 302 , that is disposed radially inward of an outward segment portion.
- the inner annular structure 308 may be situated radially inward of the outer annular structure 306 , where the radially inward indicates closer proximity to central axis A-A′.
- the MTF 112 may further comprise a plurality of vanes (e.g., 310 a and 310 b ) that extend radially outward from the inner annular structure 308 toward the outer annular structure 306 .
- Each vane may comprise a channel that houses a variety of components (e.g., support struts, air and oil service lines, and the like).
- any number of vanes may be used in the construction of an MTF 112 (e.g., 9 vanes, 18 vanes, and the like).
- a plurality of vanes may be configured to both shield high temperature intolerant components from hot gases while also imposing minimal or near minimal aerodynamic resistance.
- each of the segments (e.g., 302 and 304 ) comprising the outer annular structure 306 and/or the inner annular structure 308 may comprise a plurality of channels (e.g., 314 a , 314 b , 314 c , 314 d , 316 a , 316 b , 316 c , 316 d ) that extend axially along an axial length each of the segments.
- a plurality of channels e.g., 314 a , 314 b , 314 c , 314 d , 316 a , 316 b , 316 c , 316 d
- Each segment (e.g., 302 and 304 ) comprising the outer annular structure 306 and the inner annular structure 308 may include a plurality of tenons that define axial terminuses of each segment 302 and 304 .
- the first segment 302 may include a first and second tenon (e.g., 318 a and 318 b ) that define a first and second outer axial terminus of the first segment 302 and a third and fourth tenon (e.g., 318 c and 318 d ) that define a third and fourth inner axial terminus of the first segment 302 .
- the second segment 304 may include a first and second tenon (e.g., 320 a and 320 b ) that define a first and second outer axial terminus of the second segment 304 .
- the second segment 304 may include a third and fourth tenon (e.g., 320 c and 320 d ) that define a third and fourth inner axial terminus of the second segment.
- each segment (e.g., 302 and 304 ) comprising the MTF 112 may be coupled to an adjacent segment by a seal 312 and/or 322 .
- the second tenon 318 b of the first segment 302 may be coupled by the seal 312 to the first tenon 320 a of the second segment 304 .
- the seal 312 may thus couple or clamp the first segment 302 to the second segment 304 to form the outer annular structure 306 .
- the seal 322 may similarly couple or clamp the fourth tenon 318 d of the first segment 302 to the third tenon 320 c of the second segment 304 .
- a plurality of seals e.g., 312 and 322
- Each of the outer annular structure 306 and/or inner annular structure 308 may be overlaid by (and/or coupled to, via, e.g., the seal 312 and/or 322 ) to a perforated structure 324 (as shown with respect to the outer annular structure 306 ).
- the perforated structure 324 may comprise an arced surface that conforms or substantially conforms to the arc of the inner and/or outer annular structures 306 and/or 308 .
- the perforated structure may further comprise any of a variety of temperature resistant materials and/or alloys, and may comprise primarily sheet metal in nature.
- vanes 310 a and 310 b may pass through the MTF 112 duct, through which combustion gasses may flow at high velocity and temperature.
- cooling may be desired.
- cooling air may be pumped in from, for example, an outer portion of the MTF 112 , such that it impinges on the perforated structure 324 . As this occurs, the air may pass through the perforated structure 324 (due to a difference in pressure) to cool each of the first segment 302 and second segment 304 of the outer annular structure 306 .
- central axis A-A′ is shown with respect to segments 302 and 304 .
- Vanes 310 a and 310 b are shown disposed in gas flow 402 .
- Gas flow 402 may flow in a volume bounded by surface 408 and 410 .
- Vanes 310 a and 310 b are shaped so as to reduce aerodynamic resistance.
- the curved profile of vanes 310 a and 310 b may tend to reduce drag.
- Vane 310 b defines channel 412 that extends radially toward central axis A-A′.
- One or more high temperature intolerant components may be disposed along or at least partially along channel 412 so that vane 310 b provides thermal and/or aerodynamic protection to the one or more high temperature intolerant components.
- Vanes 310 a and 310 b may vary in radial length from forward to aft.
- the radial length of vane 310 a at its most forward position is shown as length 404 .
- the radial length of vane 310 a at its most aft position is shown as length 406 .
- length 404 is less than length 406 .
- Vanes 310 a and 310 b may comprise any material suitable for providing thermal and/or aerodynamic protection to one or more high temperature intolerant components.
- vanes 310 a and 310 b may comprise nickel, cobalt, and other metals and/or metal alloys.
- vane 310 b is shown extending between radially outward arc segment 504 and radially inward arc segment 502 . Vane 310 b defines channel 412 .
- High temperature intolerant component 506 is shown disposed in channel 412 .
- High temperature intolerant component 506 may comprise, for example, one or more of air and oil service lines and/or support struts.
- references to “one embodiment,” “an embodiment,” “an example embodiment,” etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The present disclosure relates to a vane for a jet engine mid-turbine frame, and more particularly, to a vane for a jet engine mid-turbine frame vane segment.
- Gas turbine engines (e.g., jet engines) generally include a compressor to pressurize inflowing air, a combustor to burn a fuel in the presence of the pressurized air, and a turbine to extract energy from the resulting combustion gases. The compressor may comprise a low pressure compressor, as well as a high pressure compressor. The turbine may likewise comprise a high pressure turbine and a low pressure turbine.
- In various embodiments, an apparatus is provided comprising a radially outward segment portion, a radially inward segment portion, and a vane that extends between the radially outward segment portion and the radially inward segment portion.
- In various embodiments, a mid-turbine frame (“MTF”) for a jet engine is provided comprising a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure is situated radially inward of the outer annular structure and a vane that extend radially outward from the inner annular structure through the outer annular structure.
- The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. A more complete understanding of the present disclosure, however, may best be obtained by referring to the detailed description and claims when considered in connection with the drawing figures, wherein like numerals denote like elements.
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FIG. 1 illustrates, in accordance with various embodiments, a cutaway view of a jet engine; -
FIG. 2 illustrates, in accordance with various embodiments, a cross-sectional view of portion of a jet engine turbine; -
FIG. 3 illustrates, in accordance with various embodiments, a cutaway view of a MTF; -
FIG. 4 illustrates, in accordance with various embodiments, a perspective view of vanes of an MTF; and -
FIG. 5 illustrates, in accordance with various embodiments, a further perspective view of vanes of an MTF. - The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration and their best mode. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the inventions, it should be understood that other embodiments may be realized and that logical, chemical and mechanical changes may be made without departing from the spirit and scope of the inventions. Thus, the detailed description herein is presented for purposes of illustration only and not of limitation. For example, the steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented. Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact.
- As used herein, “aft” refers to the direction associated with the tail (e.g., the back end) of an aircraft, or generally, to the direction of exhaust of the gas turbine. As used herein, “forward” refers to the directed associated with the nose (e.g., the front end) of an aircraft, or generally, to the direction of flight or motion. For example, with reference to
FIG. 1 , central axis A-A′ may be described as extending from a forward position (A) to an aft position (A′). - A gas turbine engine may comprise a high pressure turbine and a low pressure turbine. Hot gas from a combustion section of a gas turbine engine may flow into the high pressure turbine and the low pressure turbine, in that order, from forward to aft. The kinetic energy of the hot gas is captured by the high pressure turbine and the low pressure turbine and converted into more other useful forms of energy. High pressure turbines tend to operate at maximum efficiency when the gas is hot and the high pressure turbine is small. Low pressure turbines tend to work at maximum efficiency when the hot gases operate at the low pressure turbine's largest diameter. Thus, for improved efficiency, there may be a large difference in the diameter between a high pressure turbine and a low pressure turbine. Conventionally, the forward stages of the low pressure turbine were not as efficient as they could be. However, by using or coupling a mid-turbine frame between the high pressure turbine and the low pressure turbine, the hot gases may rapidly expand as they exit the high pressure turbine to gain a large diameter upon entry into the forward stages of the low pressure turbine. For further information, U.S. Provisional Patent Application Ser. No. 61/925,001 is hereby incorporated by reference in its entirety.
- With reference now to
FIG. 1 , gas turbine engines (e.g., jet engines) 100 may extend from forward to aft along a central axis A-A′. As described above, gas turbine engines 100 generally include a compressor to pressurize inflowing air, a combustor to burn a fuel in the presence of the pressurized air, and a turbine to extract energy from the resulting combustion gases. The compressor may be divided into two sections. Specifically, the compressor may comprise alow pressure compressor 102 situated forward of ahigh pressure compressor 104. The turbine may likewise be divided into two sections. These include a high pressure turbine (or “HPT”) 106 situated forward of a low pressure turbine (or “LPT”) 108. Thecombustor 110 may be disposed axially aft of the HPT 106 and axially forward of theLPT 108. - In various embodiments, a structure, which may be referred to herein as a “mid-turbine frame” or “MTF” 112 may be included as part of the gas turbine engine 100. More particularly, as shown with respect to
FIG. 2 , the MTF 112 may be disposed aft of the HPT 106 and forward of theLPT 108. The MTF 112 may generally comprise a duct configured to convey (hot) combustion gasses from theHPT 106 to theLPT 108. The MTF 112 may thus comprise an annular and/or semi-annular duct configured, in particular, to permit the expansion of hot gasses exiting theHPT 106 into theLPT 108. The MTF 112 may enlarge in diameter as it extends from forward to aft along the central axis A-A′. - With reference to
FIG. 3 , the MTF 112 may more particularly comprise a plurality of segments (e.g., to illustrate a portion of an MTF 112, afirst segment 302 and second segment 304) that together form an MTF 112. For example, and again, to illustrate a portion of an MTF 112, thefirst segment 302 and thesecond segment 304 may comprise radially outer arcing surfaces and radially inner arcing surfaces that may be joined or sealed, as described herein, to form an outerannular structure 306 and an innerannular structure 308 of anMTF 112. Stated another way,first segment 302 andsecond segment 304 comprise arc segments that, when coupled, form outerannular structure 306 and innerannular structure 308, wherein outerannular structure 306 is radially farther from central axis A-A′ than innerannular structure 308. Specifically, thefirst segment 302 may comprise anouter arcing surface 330 a and aninner arcing surface 330 b, while thesecond segment 304 may comprise anouter arcing surface 332 a and aninner arcing surface 332 b.Outer arcing surface 332 a may be coupled to a radially outward segment portion.Inner arcing surface 332 b may be coupled to a radially inward segment portion. A radially inward segment portion may refer to a portion of a segment, such assegment 302, that is disposed radially inward of an outward segment portion. The innerannular structure 308 may be situated radially inward of the outerannular structure 306, where the radially inward indicates closer proximity to central axis A-A′. - The MTF 112 may further comprise a plurality of vanes (e.g., 310 a and 310 b) that extend radially outward from the inner
annular structure 308 toward the outerannular structure 306. Each vane may comprise a channel that houses a variety of components (e.g., support struts, air and oil service lines, and the like). In various embodiments, any number of vanes may be used in the construction of an MTF 112 (e.g., 9 vanes, 18 vanes, and the like). - It may be understood that in a gas turbine engine, various components are supported by support structures such as support struts and the like. Moreover, air and oil service lines may be along the radius of central axis A-A′ to serve various radially inward components. However, as MTF 112 is situated aft of HPT 106 and is configured to receive hot gases from HPT 106, support struts, air and oil service lines, and the like would be impaired or destroyed by hot gases from HPT 106. In various embodiments, hot gases from HPT 106 are above 900° F. Accordingly, a plurality of vanes (e.g., 310 a and 310 b) may be configured to both shield high temperature intolerant components from hot gases while also imposing minimal or near minimal aerodynamic resistance.
- In various embodiments, each of the segments (e.g., 302 and 304) comprising the outer
annular structure 306 and/or the innerannular structure 308 may comprise a plurality of channels (e.g., 314 a, 314 b, 314 c, 314 d, 316 a, 316 b, 316 c, 316 d) that extend axially along an axial length each of the segments. - Each segment (e.g., 302 and 304) comprising the outer
annular structure 306 and the innerannular structure 308 may include a plurality of tenons that define axial terminuses of eachsegment first segment 302 may include a first and second tenon (e.g., 318 a and 318 b) that define a first and second outer axial terminus of thefirst segment 302 and a third and fourth tenon (e.g., 318 c and 318 d) that define a third and fourth inner axial terminus of thefirst segment 302. - The same may be true with respect to the
second segment 304. For example, thesecond segment 304 may include a first and second tenon (e.g., 320 a and 320 b) that define a first and second outer axial terminus of thesecond segment 304. Likewise, thesecond segment 304 may include a third and fourth tenon (e.g., 320 c and 320 d) that define a third and fourth inner axial terminus of the second segment. - In various embodiments, each segment (e.g., 302 and 304) comprising the
MTF 112 may be coupled to an adjacent segment by aseal 312 and/or 322. For example, with reference toFIG. 3 , thesecond tenon 318 b of thefirst segment 302 may be coupled by theseal 312 to thefirst tenon 320 a of thesecond segment 304. Theseal 312 may thus couple or clamp thefirst segment 302 to thesecond segment 304 to form the outerannular structure 306. - The
seal 322 may similarly couple or clamp thefourth tenon 318 d of thefirst segment 302 to thethird tenon 320 c of thesecond segment 304. Thus, a plurality of seals (e.g., 312 and 322) may couple a plurality of segments (both with respect to their respective inner annular structures and outer annular structures) to form a substantially annular duct orMTF 112. - Each of the outer
annular structure 306 and/or innerannular structure 308 may be overlaid by (and/or coupled to, via, e.g., theseal 312 and/or 322) to a perforated structure 324 (as shown with respect to the outer annular structure 306). Theperforated structure 324 may comprise an arced surface that conforms or substantially conforms to the arc of the inner and/or outerannular structures 306 and/or 308. The perforated structure may further comprise any of a variety of temperature resistant materials and/or alloys, and may comprise primarily sheet metal in nature. - In operation, it may be beneficial to cool the equipment, as described above, that passes through the
vanes MTF 112 duct, through which combustion gasses may flow at high velocity and temperature. Thus, to maintain the integrity of the components within the vanes, cooling may be desired. - To achieve this result, cooling air may be pumped in from, for example, an outer portion of the
MTF 112, such that it impinges on theperforated structure 324. As this occurs, the air may pass through the perforated structure 324 (due to a difference in pressure) to cool each of thefirst segment 302 andsecond segment 304 of the outerannular structure 306. - With reference to
FIGS. 4 and 5 , central axis A-A′ is shown with respect tosegments Vanes gas flow 402.Gas flow 402 may flow in a volume bounded bysurface Vanes vanes Vane 310 b, for example, defineschannel 412 that extends radially toward central axis A-A′. One or more high temperature intolerant components may be disposed along or at least partially alongchannel 412 so thatvane 310 b provides thermal and/or aerodynamic protection to the one or more high temperature intolerant components. -
Vanes vane 310 a at its most forward position is shown aslength 404. In various embodiments, the radial length ofvane 310 a at its most aft position is shown aslength 406. In various embodiments,length 404 is less thanlength 406. -
Vanes vanes - With reference to
FIG. 5 ,vane 310 b is shown extending between radiallyoutward arc segment 504 and radiallyinward arc segment 502.Vane 310 b defineschannel 412. High temperatureintolerant component 506 is shown disposed inchannel 412. High temperatureintolerant component 506 may comprise, for example, one or more of air and oil service lines and/or support struts. - Benefits, other advantages, and solutions to problems have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the inventions. The scope of the inventions is accordingly to be limited by nothing other than the appended claims, in which reference to an element in the singular is not intended to mean “one and only one” unless explicitly so stated, but rather “one or more.” Moreover, where a phrase similar to “at least one of A, B, or C” is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C. Different cross-hatching is used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
- Systems, methods and apparatus are provided herein. In the detailed description herein, references to “one embodiment,” “an embodiment,” “an example embodiment,” etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
- Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112(f), unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprises,” “comprising,” or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Claims (15)
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US15/032,017 US10669870B2 (en) | 2014-01-28 | 2015-01-23 | Vane for jet engine mid-turbine frame |
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US201461932462P | 2014-01-28 | 2014-01-28 | |
US15/032,017 US10669870B2 (en) | 2014-01-28 | 2015-01-23 | Vane for jet engine mid-turbine frame |
PCT/US2015/012651 WO2015156889A2 (en) | 2014-01-28 | 2015-01-23 | Vane for jet engine mid-turbine frame |
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US20160258305A1 true US20160258305A1 (en) | 2016-09-08 |
US10669870B2 US10669870B2 (en) | 2020-06-02 |
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US15/032,017 Active 2036-05-02 US10669870B2 (en) | 2014-01-28 | 2015-01-23 | Vane for jet engine mid-turbine frame |
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US (1) | US10669870B2 (en) |
EP (1) | EP3099904B1 (en) |
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US11162368B2 (en) * | 2019-06-13 | 2021-11-02 | Raytheon Technologies Corporation | Airfoil assembly with ceramic airfoil pieces and seal |
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Also Published As
Publication number | Publication date |
---|---|
EP3099904B1 (en) | 2021-08-25 |
EP3099904A2 (en) | 2016-12-07 |
EP3099904A4 (en) | 2017-03-08 |
WO2015156889A2 (en) | 2015-10-15 |
WO2015156889A3 (en) | 2016-02-18 |
US10669870B2 (en) | 2020-06-02 |
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